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HQ 3.5/8 AIRFOIL (hq358-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: HQ 3.5/8 AIRFOIL (hq358-il)
Reynolds number: 100,000
Max Cl/Cd: 64.73 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq358-il-100000.txt
Download as CSV file: xf-hq358-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.5/8 AIRFOIL                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3504   0.09448   0.08988  -0.0323   1.0000   0.0608
  -7.500  -0.3564   0.09240   0.08789  -0.0311   1.0000   0.0626
  -7.250  -0.3664   0.09079   0.08638  -0.0293   1.0000   0.0637
  -7.000  -0.3795   0.08935   0.08505  -0.0273   1.0000   0.0647
  -6.750  -0.3893   0.08754   0.08333  -0.0271   1.0000   0.0659
  -6.500  -0.3971   0.08550   0.08137  -0.0295   1.0000   0.0670
  -6.250  -0.3994   0.08296   0.07880  -0.0364   1.0000   0.0679
  -6.000  -0.3964   0.08060   0.07625  -0.0424   1.0000   0.0683
  -5.750  -0.3988   0.07543   0.07139  -0.0337   1.0000   0.0702
  -5.500  -0.3966   0.07279   0.06879  -0.0312   1.0000   0.0726
  -5.250  -0.3904   0.06963   0.06562  -0.0324   1.0000   0.0761
  -5.000  -0.3640   0.06577   0.06126  -0.0453   1.0000   0.0822
  -4.750  -0.3626   0.06142   0.05718  -0.0412   1.0000   0.0842
  -4.500  -0.3525   0.05854   0.05432  -0.0405   1.0000   0.0887
  -4.250  -0.3271   0.05428   0.04975  -0.0464   1.0000   0.0975
  -4.000  -0.3071   0.05168   0.04699  -0.0480   1.0000   0.1079
  -3.750  -0.2906   0.04793   0.04325  -0.0488   1.0000   0.1146
  -3.500  -0.2676   0.04490   0.04006  -0.0509   1.0000   0.1289
  -3.250  -0.2416   0.04210   0.03701  -0.0537   1.0000   0.1528
  -3.000  -0.2198   0.03960   0.03444  -0.0547   1.0000   0.1804
  -2.250  -0.0953   0.02959   0.02213  -0.0599   1.0000   0.0664
  -2.000  -0.0528   0.02707   0.01890  -0.0617   0.9972   0.0559
  -1.750  -0.0123   0.02519   0.01685  -0.0644   0.9932   0.0605
  -1.500   0.0279   0.02359   0.01486  -0.0660   0.9884   0.0590
  -1.250   0.0688   0.02238   0.01351  -0.0680   0.9839   0.0625
  -1.000   0.1067   0.02137   0.01244  -0.0697   0.9787   0.0710
  -0.750   0.1461   0.01835   0.01165  -0.0725   0.9760   0.5991
  -0.500   0.1782   0.01772   0.01148  -0.0716   0.9692   1.0000
  -0.250   0.2140   0.01807   0.01148  -0.0737   0.9600   1.0000
   0.000   0.2544   0.01850   0.01162  -0.0766   0.9521   1.0000
   0.250   0.2949   0.01888   0.01174  -0.0796   0.9438   1.0000
   0.500   0.3297   0.01921   0.01190  -0.0814   0.9343   1.0000
   0.750   0.3709   0.01953   0.01208  -0.0842   0.9259   1.0000
   1.000   0.4155   0.01969   0.01212  -0.0875   0.9162   1.0000
   1.250   0.4582   0.01967   0.01202  -0.0901   0.9037   1.0000
   1.500   0.5025   0.01950   0.01180  -0.0927   0.8911   1.0000
   1.750   0.5430   0.01938   0.01166  -0.0948   0.8794   1.0000
   2.000   0.5833   0.01927   0.01158  -0.0968   0.8696   1.0000
   2.250   0.6322   0.01889   0.01124  -0.1001   0.8624   1.0000
   2.500   0.6663   0.01874   0.01113  -0.1007   0.8508   1.0000
   2.750   0.7012   0.01849   0.01094  -0.1014   0.8391   1.0000
   3.000   0.7365   0.01816   0.01075  -0.1019   0.8273   1.0000
   3.250   0.7713   0.01776   0.01043  -0.1021   0.8147   1.0000
   3.500   0.8047   0.01732   0.01009  -0.1021   0.8006   1.0000
   3.750   0.8375   0.01684   0.00971  -0.1017   0.7851   1.0000
   4.000   0.8707   0.01629   0.00933  -0.1013   0.7681   1.0000
   4.250   0.8976   0.01597   0.00912  -0.1000   0.7447   1.0000
   4.500   0.9255   0.01562   0.00884  -0.0987   0.7177   1.0000
   4.750   0.9521   0.01535   0.00861  -0.0972   0.6833   1.0000
   5.000   0.9766   0.01526   0.00849  -0.0954   0.6379   1.0000
   5.250   0.9994   0.01544   0.00858  -0.0935   0.5814   1.0000
   5.500   1.0202   0.01596   0.00884  -0.0915   0.5213   1.0000
   5.750   1.0403   0.01675   0.00934  -0.0898   0.4696   1.0000
   6.000   1.0606   0.01762   0.01001  -0.0883   0.4273   1.0000
   6.250   1.0812   0.01849   0.01078  -0.0870   0.3916   1.0000
   6.500   1.1019   0.01937   0.01160  -0.0857   0.3605   1.0000
   6.750   1.1209   0.02017   0.01243  -0.0842   0.3272   1.0000
   7.000   1.1335   0.02087   0.01299  -0.0819   0.2812   1.0000
   7.250   1.1434   0.02161   0.01363  -0.0795   0.2132   1.0000
   7.500   1.1418   0.02489   0.01572  -0.0755   0.0662   1.0000
   7.750   1.1459   0.02778   0.01846  -0.0718   0.0454   1.0000
   8.000   1.1570   0.02978   0.02058  -0.0691   0.0386   1.0000
   8.250   1.1672   0.03236   0.02318  -0.0667   0.0343   1.0000
   8.500   1.1848   0.03423   0.02525  -0.0650   0.0301   1.0000
   8.750   1.2054   0.03681   0.02797  -0.0639   0.0283   1.0000
   9.000   1.2288   0.03998   0.03136  -0.0630   0.0274   1.0000
   9.250   1.2501   0.04357   0.03530  -0.0620   0.0273   1.0000
   9.500   1.2655   0.04745   0.03964  -0.0602   0.0277   1.0000
   9.750   1.2717   0.05160   0.04437  -0.0575   0.0285   1.0000
  10.000   1.2693   0.05587   0.04918  -0.0543   0.0294   1.0000
  10.250   1.2613   0.06005   0.05381  -0.0510   0.0303   1.0000
  10.500   1.2480   0.06383   0.05794  -0.0475   0.0309   1.0000
  10.750   1.2318   0.06767   0.06207  -0.0446   0.0315   1.0000
  11.000   1.2138   0.07179   0.06644  -0.0425   0.0320   1.0000
  11.250   1.1945   0.07627   0.07116  -0.0415   0.0324   1.0000
  11.500   1.1743   0.08120   0.07630  -0.0417   0.0327   1.0000
  11.750   1.1535   0.08666   0.08195  -0.0430   0.0329   1.0000
  12.000   1.1318   0.09283   0.08829  -0.0456   0.0331   1.0000
  12.250   1.1099   0.09981   0.09543  -0.0496   0.0333   1.0000
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